EP0501658A1 - Contre-fiche - Google Patents

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Publication number
EP0501658A1
EP0501658A1 EP92301331A EP92301331A EP0501658A1 EP 0501658 A1 EP0501658 A1 EP 0501658A1 EP 92301331 A EP92301331 A EP 92301331A EP 92301331 A EP92301331 A EP 92301331A EP 0501658 A1 EP0501658 A1 EP 0501658A1
Authority
EP
European Patent Office
Prior art keywords
tube
strut assembly
actuator
axially
loads
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP92301331A
Other languages
German (de)
English (en)
Other versions
EP0501658B1 (fr
Inventor
Christopher Noel West
Andrew David Belben
David Michael Dunn Rees
Brian Frederick Seymour
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AgustaWestland Ltd
Original Assignee
Westland Helicopters Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Westland Helicopters Ltd filed Critical Westland Helicopters Ltd
Publication of EP0501658A1 publication Critical patent/EP0501658A1/fr
Application granted granted Critical
Publication of EP0501658B1 publication Critical patent/EP0501658B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F1/00—Springs
    • F16F1/36—Springs made of rubber or other material having high internal friction, e.g. thermoplastic elastomers
    • F16F1/366—Springs made of rubber or other material having high internal friction, e.g. thermoplastic elastomers made of fibre-reinforced plastics, i.e. characterised by their special construction from such materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/001—Vibration damping devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/001—Vibration damping devices
    • B64C2027/002—Vibration damping devices mounted between the rotor drive and the fuselage
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F2230/00—Purpose; Design features
    • F16F2230/16—Purpose; Design features used in a strut, basically rigid

Definitions

  • This invention relates to strut assemblies and particularly to strut assemblies for interconnecting parts of a structure for transmitting operational loads and for introducing forcing loads as part of an active vibration reducing system.
  • GB-A-2160840 describes an active vibration reducing system in which a plurality of force actuators are connected at or across locations between parts of a structure which are capable of relative movement at dominant vibrating forcing frequencies.
  • a number of sensors measure the vibration response at key locations on the structural part in which vibration is to be reduced and the resulting signals are fed to an adaptive computer/controller which provides optimal signals to the actuators to produce forces at the sensor locations in the structural part.
  • the actuators are pored by pulsed fluid supplies, preferably hydraulic supplies.
  • the aforementioned vibration reducing system is particularly suited for use in helicopters in that a fuselage structure in which it is desired to reduce vibration is generally constructed to be lightweight and flexible and is attached beneath a gearbox and rotor structure that has a high mass and is constructed to be as rigid as possible.
  • a fuselage structure in which it is desired to reduce vibration is generally constructed to be lightweight and flexible and is attached beneath a gearbox and rotor structure that has a high mass and is constructed to be as rigid as possible.
  • an exemplary embodiment of GB-A-2160840 envisages connecting the force actuators between the gearbox and the fuselage although it is clear that other locations are possible.
  • the actuators can alternatively be connected between the fuselage structure at one point and a seismic mass to generate the required forcing.
  • Such a system is termed a single point actuation system.
  • FIG. 7 of that specification discloses a strut assembly incorporating an electro-hydraulic jack straddling an oblate oval elastic ring which in operation is required to transmit primary lift and manoeuvring loads whilst permitting the jack to input forcing loads to reduce vibration.
  • the oval elastic ring represents an inefficient primary load path and it is difficult to tailor the bending loads in the ring to suit operational requirements in respect of both mechanical strength and elastic properties.
  • the elastic ring requires a large space envelope and is bulky and heavy which may also frustrate installation in some applications.
  • An objective of this invention is therefore to provide a strut assembly which overcomes the aforementioned problems.
  • this invention provides a strut assembly for interconnecting two parts of a structure for transmitting operational loads between the parts and for inputting periodic loads to at least one of the parts, said strut assembly comprising an axially elastically extensible tube having attachment means at each end for attaching said strut assembly between said parts and an axially extensible actuator attached within the tube between its ends, the axial stiffness of the tube being selected so that reciprocal axial extensions of the actuator cause elastic longitudinal displacements of the strut assembly to input said periodic loads.
  • the actuator may extend coaxially within the tube and may comprise a body portion attached to the attachment means at one end of the tube and an actuator ram attached to the attachment means at the other end.
  • the actuator body portion may be attached to an annular surface at an inner end of a tubular support member extending coaxially within the tube from said attachment means.
  • the actuator may comprise an electro-hydraulic actuator.
  • the axially elastically extensible tube is manufactured from fibre reinforced plastics materials.
  • this invention provides a strut assembly for interconnecting two parts of a structure for transmitting operational loads between the parts and for inputting periodic loads to at least one of said parts, said strut assembly comprising an axially elastically extensible tube having attachment means at one end for attachment to one of said structural parts and its other end attached to a support member having attachment means for connection to the other of said structural parts, an axially extensible actuator attached co-axially in the tube between said support member and the end of the tube, the axial stiffness of the tube being selected so that reciprocal extensions of the actuator cause elastic longitudinal displacements of the strut assembly to input said periodic loads.
  • this invention provides a strut assembly for connecting a gearbox to a helicopter fuselage for transmitting flight loads from the gearbox to the fuselage and for inputting periodic forcing loads into the gearbox as part of an active vibration control system, said strut assembly comprising an axially elastically extensible tube having attachment means at its ends for attachment respectively to said gearbox and fuselage, an axially extensible actuator attached co-axially within the tube between its ends, the axial stiffness of the tube being selected to be capable of transmitting operational loads and so that reciprocal extensions of the actuator cause elastic longitudinal displacements of the strut assembly to input said periodic forcing loads.
  • a helicopter generally indicated at 11 has a fuselage 12 carrying a gearbox 13 driving a main sustaining rotor 14 about a generally vertical axis 15.
  • Gearbox 13 is supported from the fuselage 12 by four strut assemblies 16 (two only being shown) attached between the gearbox 13 and fuselage 12.
  • Each of the strut assemblies 16 transmits primary flight and manoeuvring loads from the gearbox 13 to the fuselage 12.
  • each of the strut assemblies 16 incorporates an electro-hydraulic actuator 24 as hereinafter described, the actuators being connected to a controller 17 of an active vibration control system for inputting forcing loads as described in the aforementioned GB-A-2160840.
  • each strut assembly 16 includes an axially elastically extensible tube 18 manufactured from fibre reinforced plastics materials and having attachment means comprising apertured end fitting 19 bolted into one end to facilitate attachment to the gearbox 13.
  • the other end of tube 18 is bolted to an external surface of a generally tubular co-axial support member 20 having an integral apertured end fitting 21 for attachment to the fuselage 12.
  • the tubular end of support member 20 extends co-axially within tube 18 to terminate at an inner annular surface 22 partially along the length of tube 18.
  • a body portion 23 of the electro-hydraulic actuator 24 is bolted to the inner surface 22 of support member 20 through an integral flange 25 so as to extend co-axially in respect of the tube 18.
  • An outer end of an actuator ram 26 of actuator 24 is bolted centrally to the end fitting 19 at the end of tube 18.
  • Hydraulic supply and return lines (not sheets) are connected respectively to ports 27 and 28 extending radially from the body portion 23 and protruding through clearance holes 33 in the support member 20 and clearance holes 34 in the tube 18. Electrical signals from controller 17 ( Figure 1) are supplied to the actuator 24 through a cable 29 routed through an aperture in the wall of support member 20.
  • the stiffness characteristics of the axially elastically extensible tube 18 are determined for each particular application and are achieved by the choice of materials used in its manufacture and, in the case of fibre-reinforced materials, the particular lay-up of such materials.
  • the basic tube 18 of the illustrated embodiment comprises fourteen layers of unidirectional glass reinforcing fibres in a polymer matrix.
  • the glass fibres are 'S' glass fibres and the polymer is a thermoplastic polyetheretherketone (PEEK) resin.
  • Seven of the plies are arranged with the fibres at 0 degrees to the longitudinal axis of the tube 18 and seven plies are arranged with the fibres at ⁇ 45 degrees.
  • the outer end of tube 18 which is attached to end fitting 19 ( Figure 2) is thickened internally at 31 by an additional twenty eight plies with the fibres arranged at both 0 and ⁇ 45 degrees, and the other end is thickened externally at 32 by a similar amount.
  • fibre reinforced plastics materials facilitates the manufacture of the tube 18 and ensures it has the necessary mechanical strength and elastic properties in order for the strut assembly 16 to perform its operational functions.
  • the tube 18 has sufficient mechanical strength to enable the strut assembly 16 to provide support between the helicopter fuselage 12 and gearbox 13 in order to sustain the lift and manoeuvre loads emanating from the sustaining rotor 14. Furthermore, the elastic properties of the tube 18 provide appropriate axial elastic extensibility such that the actuator 24 mounted in parallel and signalled from the controller 17 of the active vibration control system can input the displacements to introduce forcing loads into the strut assembly 16 by axial elastic extension of the tube 18 to control the dynamic response of fuselage 12 in the manner disclosed in GB-A-2160840.
  • the strut assembly 16 of this invention provides a simple, compact and lightweight device.
  • the use of an axially elastically extensible tube 18 in parallel with the actuator 24 provides an efficient primary load path and the tube 18 can be readily tailored during manufacture to provide optimum mechanical strength and elastic properties.
  • the fibre reinforced tube 18 of the illustrated embodiment can be manufactured using any available techniques such as moulding using an inflatable inner mandrel and a female mould tool, and the fibre reinforced material can be in the form of pre-impregnated sheets or in the form of continuous fibres laid using available automated winding techniques.
  • the strut assembly 16 of this invention can be used to good effect in other installations incorporating active vibration reducing systems.
  • the strut assembly 16 could be used to support the engines in the engine bays of fixed wing aircraft to reduce fuselage vibration as well as in land or sea vehicles or in fixed installations.
  • the strut assembly 16 of this invention can be used in both dual point and single point actuation system and, in the latter type systems, it will be understood that the mass comprises one of the two structural parts interconnected by the strut assembly 16.
  • the axially extensible tube 18 can be manufactured from metal for example titanium.
  • Other suitable forms of actuator can be used in place of the electrohydraulic actuator 24 of the described embodiment.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Vibration Prevention Devices (AREA)
  • Springs (AREA)
EP92301331A 1991-02-28 1992-02-19 Contre-fiche Expired - Lifetime EP0501658B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB919104190A GB9104190D0 (en) 1991-02-28 1991-02-28 Strut assemblies
GB9104190 1991-02-28

Publications (2)

Publication Number Publication Date
EP0501658A1 true EP0501658A1 (fr) 1992-09-02
EP0501658B1 EP0501658B1 (fr) 1995-01-11

Family

ID=10690719

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92301331A Expired - Lifetime EP0501658B1 (fr) 1991-02-28 1992-02-19 Contre-fiche

Country Status (6)

Country Link
US (1) US5269489A (fr)
EP (1) EP0501658B1 (fr)
JP (1) JP3471822B2 (fr)
CA (1) CA2061823C (fr)
DE (1) DE69201142T2 (fr)
GB (1) GB9104190D0 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0542453A1 (fr) * 1991-11-13 1993-05-19 Westland Helicopters Limited Contre-fiche
FR2689951A1 (fr) * 1992-04-10 1993-10-15 Bertin & Cie Dispositif de liaison mécanique rigide à coupure de fréquence.
GB2276690A (en) * 1993-04-02 1994-10-05 Deutsche Forsch Luft Raumfahrt Actively-adjustable connecting rods
EP0930443A2 (fr) * 1998-01-14 1999-07-21 Deutsches Zentrum für Luft- und Raumfahrt e.V. Procédé de fabrication d'une bielle très chargée et bielle obtenue selon ce procédé
EP1724191A1 (fr) * 2005-05-16 2006-11-22 Agusta S.p.A. Hélicoptère avec dispositif de controle de vibrations amélioré
EP2439425A1 (fr) * 2010-10-11 2012-04-11 Airbus Operations Dispositif de liaison de sécurité et aéronef équipé d?un tel dispositif de liaison de sécurité
EP3194264A4 (fr) * 2014-08-07 2018-03-21 Sikorsky Aircraft Corporation Système d'actionnement d'aéronef produisant une charge anti-vibrations

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5435531A (en) * 1993-08-18 1995-07-25 Bell Helicopter Textron Inc. Vibration isolation system
KR19990044364A (ko) * 1996-07-09 1999-06-25 오오시마 야스히로 노광용 헤드 및 인쇄장치
US6229898B1 (en) 1998-12-23 2001-05-08 Sikorsky Aircraft Corporation Active vibration control system using on-line system identification with enhanced noise reduction
US6416016B1 (en) 2000-09-15 2002-07-09 Sikorsky Aircraft Corporation Actuator for an active transmission mount isolation system
US6634862B2 (en) 2000-09-15 2003-10-21 General Dynamics Advanced Information Systems, Inc. Hydraulic actuator
US6467723B1 (en) 2000-10-10 2002-10-22 Lord Corporation Active vibration control system for helicopter with improved actustor placement
US20050056117A1 (en) * 2003-07-22 2005-03-17 Kaiser Compositek, Inc. Composite strut and method of making same
US7128293B2 (en) * 2003-12-04 2006-10-31 Reggald Emory Isley Helicopter
WO2008060681A2 (fr) * 2006-05-06 2008-05-22 Lord Corporation Bras profilé axial d'isolateur d'hélicoptère à vibration réduite
EP2241502B1 (fr) * 2009-04-13 2017-03-08 Sikorsky Aircraft Corporation Suppression des vibrations actives par minimisation de la puissance
US8091481B1 (en) 2009-05-01 2012-01-10 Floyd Brian A Gas strut separation for staged rocket
US9797257B2 (en) 2012-12-10 2017-10-24 General Electric Company Attachment of composite article
US9777579B2 (en) 2012-12-10 2017-10-03 General Electric Company Attachment of composite article

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1182339A (en) * 1966-09-16 1970-02-25 Sud Aviation Improvements in or relating to Rotary-wing Aircraft
US3635427A (en) * 1969-05-06 1972-01-18 Textron Inc Aircraft vibration compensation system

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4546960A (en) * 1983-06-20 1985-10-15 Gould Inc. Vibration isolation assembly
US4536114A (en) * 1983-07-01 1985-08-20 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Variable length strut with longitudinal compliance and locking capability
US4819182A (en) * 1985-06-21 1989-04-04 Westland Plc Method and apparatus for reducing vibration of a helicopter fuselage
US4901486A (en) * 1987-03-06 1990-02-20 Kajima Corporation Elasto-plastic damper
US4848525A (en) * 1987-11-02 1989-07-18 The Boeing Company Dual mode vibration isolator
FR2629545B1 (fr) * 1988-03-30 1993-02-19 Aerospatiale Contre-fiche elastique a resonateur hydro-mecanique integre notamment pour la suspension d'une boite de transmission sur un giravion et dispositif de suspension en comportant application
DE3921824A1 (de) * 1988-07-11 1990-04-19 Takenaka Corp Daempfungssockel
US5087491A (en) * 1990-02-09 1992-02-11 The United States Of America As Represented By The Secretary Of The Navy Vibration-damping structural member

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1182339A (en) * 1966-09-16 1970-02-25 Sud Aviation Improvements in or relating to Rotary-wing Aircraft
US3635427A (en) * 1969-05-06 1972-01-18 Textron Inc Aircraft vibration compensation system

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0542453A1 (fr) * 1991-11-13 1993-05-19 Westland Helicopters Limited Contre-fiche
FR2689951A1 (fr) * 1992-04-10 1993-10-15 Bertin & Cie Dispositif de liaison mécanique rigide à coupure de fréquence.
WO1993021460A1 (fr) * 1992-04-10 1993-10-28 Bertin & Cie Dispositif de liaison mecanique rigide a coupure de frequence
US5568847A (en) * 1992-04-10 1996-10-29 Bertin & Cie Device for providing a rigid mechanical link with frequency cut-off
GB2276690A (en) * 1993-04-02 1994-10-05 Deutsche Forsch Luft Raumfahrt Actively-adjustable connecting rods
GB2276690B (en) * 1993-04-02 1996-05-01 Deutsche Forsch Luft Raumfahrt Connecting rods
US5542230A (en) * 1993-04-02 1996-08-06 Deutsche Forschungsanstalt F. Luft-Und Raumfahrt E.V. Connecting rods
EP0930443A3 (fr) * 1998-01-14 2000-06-21 Deutsches Zentrum für Luft- und Raumfahrt e.V. Procédé de fabrication d'une bielle très chargée et bielle obtenue selon ce procédé
EP0930443A2 (fr) * 1998-01-14 1999-07-21 Deutsches Zentrum für Luft- und Raumfahrt e.V. Procédé de fabrication d'une bielle très chargée et bielle obtenue selon ce procédé
EP1724191A1 (fr) * 2005-05-16 2006-11-22 Agusta S.p.A. Hélicoptère avec dispositif de controle de vibrations amélioré
US7857255B2 (en) 2005-05-16 2010-12-28 Agusto S.P.A. Helicopter with an improved vibration control device
JP2012136219A (ja) * 2005-05-16 2012-07-19 Agustawestland Spa 改良型振動制御装置を備えたヘリコプタ
EP2439425A1 (fr) * 2010-10-11 2012-04-11 Airbus Operations Dispositif de liaison de sécurité et aéronef équipé d?un tel dispositif de liaison de sécurité
FR2965850A1 (fr) * 2010-10-11 2012-04-13 Airbus Operations Sas Dispositif de liaison de securite et aeronef equipe d’un tel dispositif de liaison de securite
US9086113B2 (en) 2010-10-11 2015-07-21 Airbus Operations S.A.S. Safety link device and aircraft equipped with such a safety link device
EP3194264A4 (fr) * 2014-08-07 2018-03-21 Sikorsky Aircraft Corporation Système d'actionnement d'aéronef produisant une charge anti-vibrations
US10745116B2 (en) 2014-08-07 2020-08-18 Sikorsky Aircraft Corporation Anti-vibration load generating aircraft actuation system

Also Published As

Publication number Publication date
GB9104190D0 (en) 1991-06-12
EP0501658B1 (fr) 1995-01-11
JP3471822B2 (ja) 2003-12-02
JPH04327040A (ja) 1992-11-16
US5269489A (en) 1993-12-14
DE69201142D1 (de) 1995-02-23
CA2061823A1 (fr) 1992-08-29
DE69201142T2 (de) 1995-07-27
CA2061823C (fr) 2001-12-25

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